| 高超声速飞行器后体/尾喷管一体化设计 |
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| 引用本文： | 车竞,唐硕.高超声速飞行器后体/尾喷管一体化设计[J].飞行力学,2006,24(3):74-77. |
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| 作者姓名： | 车竞 唐硕 |
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| 作者单位： | 西北工业大学,航天学院,陕西,西安,710072 |
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| 基金项目： | 国家自然科学基金;国防科技应用基础研究基金 |
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| 摘 要： | 采用实数编码、小生境技术、稳态复制策略、多目标定级排序技术,改进了标准遗传算法,建立了多目标遗传算法,并将其应用于高超声速飞行器后体/尾喷管的一体化设计,以尾喷管的推力、升力和附加俯仰力矩系数为性能目标,得到了优化问题的Pareto最优前沿面,优化结果显示了设计变量与性能目标之间的关系,并提出了建议的外形方案。该优化算法可进一步推广应用于包含更加精确的流动模型的优化设计当中。
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| 关 键 词： | 高超声速飞行器 后体/尾喷管 一体化设计 遗传算法 |
| 文章编号： | 1002-0853(2006)03-0074-04 |
| 收稿时间： | 2005-09-22 |
| 修稿时间： | 2006-04-14 |
The Application of Genetic Algorithms to Afterbody/Nozzle Integrated Design of a Hypersonic Vehicle |
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| CHE Jing,TANG Shuo.The Application of Genetic Algorithms to Afterbody/Nozzle Integrated Design of a Hypersonic Vehicle[J].Flight Dynamics,2006,24(3):74-77. |
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| Authors: | CHE Jing TANG Shuo |
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| Abstract: | Through adopting the real number coding,niche technique, steady reproduce strategy and multi-objective class & rank skill,this paper improves simple genetic algorithms to multi-objective genetic algorithms,which are applied in the integrated design of afterbody/nozzle of a hypersonic vehicle.In the optimization question,thrust coefficient,lift coefficient and pitching moment coefficient of nozzle are as the performance objects,and the Pareto front is gotten.The optimization result shows the relationship of design variables and performance objects,and the recommended shape project is presented.As a method,this algorithm can be applied in the optimization design with a more accurate flow model. |
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| Keywords: | hypersonic vehicle afterbody/nozzle integrated design genetic algorithms |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
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